Static Aeroelastic Modeling of a Sub-Scale Wind Tunnel Model with Novel Flap Concept

Ting, Eric B.; Nguyen, Nhan T.; Lebofsky, Sonia

doi:10.2514/6.2015-1407

Cited by 3 publications

(2 citation statements)

References 15 publications

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“…The deformation capability of the geometry tool allows a finite-element model to couple directly to Vorview for coupled aerodynamic-structural modeling. 16 …”

Section: Coupled Aerodynamic-structural Modelingmentioning

confidence: 97%

Aeroelastic Analysis of Wind Tunnel Test Data of a Flexible Wing with a Variable Camber Continuous Trailing Edge Flap (VCCTEF)

Nguyen

Ting

Lebofsky

2015

56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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This paper presents data analysis of a flexible wing wind tunnel model with a variable camber continuous trailing edge flap (VCCTEF) design for drag minimization tested at the University of Washington Aeronautical Laboratory (UWAL). The wind tunnel test was designed to explore the relative merit of the VCCTEF concept for improved cruise efficiency through the use of low-cost aeroelastic model test techniques. The flexible wing model is a 10%-scale model of a typical transport wing and is constructed of woven fabric composites and foam core. The wing structural stiffness in bending is tailored to be half of the stiffness of a Boeing 757-era transport wing while the torsional stiffness is about the same. This stiffness reduction results in a wing tip deflection of about 10% of the wing semi-span. The VCCTEF is a multi-segment flap design having three chordwise camber segments and five spanwise flap sections for a total of 15 individual flap elements. The three chordwise camber segments can be positioned appropriately to create a desired trailing edge camber. Elastomeric material is used to cover the gaps in between the spanwise flap sections, thereby creating a continuous trailing edge. Wind tunnel data analysis conducted previously shows that the VCCTEF can achieve a drag reduction of up to 6.31% and an improvement in the lift-to-drag ratio (L/D) of up to 4.85%. A method for estimating the bending and torsional stiffnesses of the flexible wing UWAL wind tunnel model from static load test data is presented. The resulting estimation indicates that the stiffness of the flexible wing is significantly stiffer in torsion than in bending by as much as 3 to 1. The lift prediction for the flexible wing is computed by a coupled aerodynamic-structural model. The coupled model is developed by coupling a conceptual aerodynamic tool Vorlax with a finite-element model of the flexible wing via an automated geometry deformation tool. Based on the comparison of the lift curve slope, the lift prediction for the rigid wing is in good agreement with the estimated lift coefficients derived from the wind tunnel test data. Due to the movement of the VCCTEF during the wind tunnel test, uncertainty in the lift prediction due to the indicated variations of the VCCTEF deflection is studied. The results show a significant spread in the lift prediction which contradicts the consistency in the aerodynamic measurements, thus suggesting that the indicated variations as measured by the VICON system may not be reliable. The lift prediction of the flexible wing agrees very well with the measured lift curve for the baseline configuration. The computed bending deflection and wash-out twist of the flexible wing also match reasonably well with the aeroelastic deflection measurements. The results demonstrate the validity of the aerodynamic-structural tool for use to analyze aerodynamic performance of flexible wings.

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“…The deformation capability of the geometry tool allows a finite-element model to couple directly to Vorview for coupled aerodynamic-structural modeling. 16 …”

Section: Coupled Aerodynamic-structural Modelingmentioning

confidence: 97%

Aeroelastic Analysis of Wind Tunnel Test Data of a Flexible Wing with a Variable Camber Continuous Trailing Edge Flap (VCCTEF)

Nguyen

Ting

Lebofsky

2015

56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…A static aeroelasticity framework is used to couple the aerodynamics model to a finite-element analysis to appropriately deform the aircraft wing for a given set of operating conditions using an iterative tool similar to past studies. 9,11,20,37 A geometry deformer is used in order to aeroelastically deform outer mold line geometry for input into the aerodynamic analysis tool. Figure 4 shows a high level representation of the coupling implemented in the MATLAB aeroelasticity framework.…”

Section: Static Aeroelasticity Modelmentioning

confidence: 99%

Aerodynamic Modeling of Transonic Aircraft Using Vortex Lattice Coupled with Transonic Small Disturbance for Conceptual Design

Chaparro¹,

Fujiwara

Ting

et al. 2016

34th AIAA Applied Aerodynamics Conference

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The need to rapidly scan large design spaces during conceptual design calls for computationally inexpensive tools such as the vortex lattice method (VLM). Although some VLM tools, such as Vorview have been extended to model fully-supersonic flow, VLM solutions are typically limited to inviscid, subcritical flow regimes. Many transport aircraft operate at transonic speeds, which limits the applicability of VLM for such applications. This paper presents a novel approach to correct three-dimensional VLM through coupling of two-dimensional transonic small disturbance (TSD) solutions along the span of an aircraft wing in order to accurately predict transonic aerodynamic loading and wave drag for transport aircraft. The approach is extended to predict flow separation and capture the attenuation of aerodynamic forces due to boundary layer viscosity by coupling the TSD solver with an integral boundary layer (IBL) model. The modeling framework is applied to the NASA General Transport Model (GTM) integrated with a novel control surface known as the Variable Camber Continuous Trailing Edge Flap (VCCTEF).

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Static Aeroelastic Model Assessment in the Transonic Regime

Denison

Ting

Housman

et al. 2016

34th AIAA Applied Aerodynamics Conference

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Static Aeroelastic Modeling of a Sub-Scale Wind Tunnel Model with Novel Flap Concept

Cited by 3 publications

References 15 publications

Aeroelastic Analysis of Wind Tunnel Test Data of a Flexible Wing with a Variable Camber Continuous Trailing Edge Flap (VCCTEF)

Aeroelastic Analysis of Wind Tunnel Test Data of a Flexible Wing with a Variable Camber Continuous Trailing Edge Flap (VCCTEF)

Aerodynamic Modeling of Transonic Aircraft Using Vortex Lattice Coupled with Transonic Small Disturbance for Conceptual Design

Static Aeroelastic Model Assessment in the Transonic Regime

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